0 Hamilton Sundstrand 

A United Technologies Company 

MAINTENANCE MANUAL 

14RF-9 

Information Subject to Export Control Laws 

P5186 

The technical data in this document (or file) Is controlled for export under the Export Administration Regulations (EAR), 15 CFR 

Parts 730-774. VIolations of these Jaws may be subject to fines and penalties under the Export Administration Act 

EAR Export Classification: ECCN 9E991 

VARIABLE PITCH AIRCRAFT 

PROPELLER 

14RF-9 PROPELLER MODEL 

PART NUMBER 

780100 

© 1984-1986, 1988, 1994, 1995, 1998, 1999, 2005,2006,2012 Hamilton Sundstrand Corporation 

PROPRIETARY 

THIS DOCUMENT AND THE INFORMATION CONTAINED HEREIN ARE THE PROPERTY OF HAMILTON SUNDSTRAND 

CORPORATION (HSC). RECIPIENT AGREES TO HOLD ALL SUCH INFORMATION IN CONFIDENCE AND AGREES IT SHALL BE 

USED ONLY FOR RECIPIENT'S INTERNAL PURPOSES TO MAINTAIN RECIPIENT'S EQUIPMENT OR AS MAY OTHERWISE BE 

PERMITTED IN AN APPLICABLE AGREEMENT BETWEEN RECIPIENT AND HSC. THIS DOCUMENT AND THE INFORMATION 

CONTAINED HEREIN SHALL NOT BE USED FOR ANY OTHER PURPOSE, INCLUDING THE CREATION, MANUFACTURE, 

DEVELOPMENT, OR DERIVATION OF ANY REPAIRS, MODIFICATIONS, SPARE PARTS, DESIGN, OR CONFIGURATION CHANGES, 

OR TO OBTAIN FAA OR ANY OTHER GOVERNMENT OR REGULATORY APPROVAL FOR SAME. RECIPIENT AGREES NOT TO 

DISCLOSE SUCH INFORMATION TO ANY THIRD PARTY, EXCEPT AS MAY OTHERWISE BE PROVIDED FOR IN AN APPLICABLE 

AGREEMENT BETWEEN RECIPIENT AND HSC. COPYING OR DISCLOSURE OF THIS DOCUMENT AND THE INFORMATION 

CONTAINED HEREIN BY ANYONE WITHOUT HSC'S PRIOR WRITTEN PERMISSION IS NOT AUTHORIZED AND MAY RESULT IN 

CRIMINAL AND/OR CIVIL LIABILITY 

The data in this document were developed only to maintain systems and/or parts manufactured by or for Hamilton Sundstrand or approved 

by Hamilton Sundstrand. The data may not be applicable to any other systems and/or parts, regardless of their apparent similarity to 

systems and/or parts manufactured by or for Hamilton Sundstrand or approved by Hamilton Sundstrand. Do not rely in any way on data in 

this document to maintain or otherwise support systems and/or parts that were not manufactured by or for Hamilton Sundstrand or approved by Hamilton Sundstrand without evidence that the Federal Aviation Administration or other regulatory agency has determined that the data 

in this document is valid for such use. 

PROPELLER SYSTEM MAINTENANCE MANUAL 

AIRWORTHINESS LIMITATIONS· FAA APPROVED 

REMAINDER OF MANUAL • FAA ACCEPTED 

Basic Issue: 

CAGE Code: 73030 61 Revision 12 

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0 Hamilton Sundstrand 

A United Technologies Company 

MAINTENANCE MANUAL 

14RF-9 

AIRWORTHINESS LIMITATIONS 

WARNING: THIS SECTION CONTAINS DESIGN CRITICAL CHARACTERISTICS AND 

PROCESSES. THESE ARE IDENTIFIED WITH THE SYMBOL >>DCC<<. REFER 

TO THE INTRODUCTION OF THIS MANUAL FOR A COMPLETE EXPLANATION 

OF DESIGN CRITICAL CHARACTERISTICS. 

u 

1. General 

A. The Airworthiness Limitations section is FAA approved and specifies maintenance 

required under§§ 43.16 and 91.403 of the Federal Aviation Regulations unless an 

alternative program has been FAA approved. 

2. Mandatory Inspections 

A. Major Propeller Inspection 

(1) Refer to the CHECK section of the Component Maintenance Manual61-13-04 for 

the instructions on how to do a major propeller inspection. 

(2) The major inspection intervals are listed in Table AL-1 . It is the responsibility of the 

aircraft operator to monitor flight hours for each component listed in Table AL-1 and 

to make sure that no component remains in service beyond the listed inspection 

interval times or any designated component life limits 

(3) In addition to the published operating time limits for blades and hubs, the 

requirement for repetitive Ml of these components will be no later than seven (7) 

years (or 84 months) since the Date Since Installation (DSI). The DSI will begin upon 

the initial installation after the most recent Ml or initial installation after production. 

(4) Propeller blades and hubs must now be subjected to Ml based on published 

operating time limits for the component or 7 years from the DSI whichever comes 

first. 

Table AL-1. Major Inspection Intervals 

Inspection Inspection 

Interval Item Part Number Interval (Calendar (Flight Hours) Time) 

Propeller Hub 782501-4, 782501-6, 782501-7, 9,000 7 Years 

814721-1, 814721-2 

Outer Bearing Race * 782674-1 9,000 Not Applicable 

Inner Bearing Race 782676-1 10,000 Not Applicable 

(two-piece) 

Blade and Pin RFC11E1-6A, RFC11M1-6A, 10,000 7 Years 

Assembly RFC11N1-6A, RFC11U1-6A, 

RFC11AA1-6A, RFC11E1R6A, 

RFC11M1R6A, RFC11M1P6A, 

RFC11N1R6A,RFC11U1R6A, 

RFC11U1P6A, RFC11AA1P6A, 

RFC11AA1R6A 

se or a1sctosure or m1s aata 1s suo1ect to resmctJons on me 11~e 1-'a g e or tms aocument. 

Use or disclosure of this data is subject to restrictions on the Title Page of this document. 

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Hamilton Sundstrand 

A United Technologies Company 

MAINTENANCE MANUAL 

14RF-9 

Table AL-1. Major Inspection Intervals 

Inspection 

Part Number Interval 

(Flight Hours) 

Inspection 

Interval 

(Calendar 

Time) 

Actuator Assembly 790201-2, 790201-3, 10,000 Not applicable 

790201-5, 790201-6, 

790201-7, 790201-8 

* >>DCC<< The outer bearing race must be removed, discarded and replaced at each major 

inspection interval (see CHECK section of Component Maintenance Manual61-13-04). It is 

permissible to use the propeller hub time to track the outer bearing races total time. 

B. Critical Part Inspections 

(1) The components listed in Table AL-2 require inspection to assure continued 

airworthiness. Component assemblies must be removed from service and subjected 

to the required inspections. 

(2) Critical Part Inspections accomplished in accordance with the CHECK section of the 

applicable Component Maintenance Manual, at the intervals given in Table AL-2, 

satisfy the requirements of Airworthiness Directive (AD) 96-25-20 as an alternate 

method of compliance as approved by letter from the Manager, FAA Boston Aircraft 

Certification Office, on June 3, 1999. 

(3) It is the responsibility of the operator to monitor the flight hours for each component 

listed in Table AL-2. 

Use or disclosure of this data is subject to restrictions on the Trtle Page of this document 

Use or disclosure of this data is subject to restrictions on the Title Page of this document. 

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A United Technologies Company 

MAINTENANCE MANUAL 

14RF-9 

Table AL-2. Propeller Components With Mandatory Inspections 

Item Part Number Inspection Interval 

(Flight Hours) 

A!;;tygtQr A§§~mbl~ * 790201-21 -31 -51 -6, Maximum 10,500 hour intervals. 

-7,-8 

Qil Trgn§f~r Tyb~ gng R~tgin~r * 784525-2 Initial Inspection*** within 61000 hours 

or 3 years after the effective date of 

790202-11 -2, -3, AD 96-25-20 (February 71 1997). 

814782-11 -2, -3 Repeat Inspection - Maximum 101500 

hour intervals. 

Prog~ll~r Qgntrgl Unit** (PCU) 782490-71 -12, -24, Initial Inspection*** within 6000 hours 

* 

** 

*** 

-35, -46 or 3 years after the effective date of 

AD 96-25-20 (February 7, 1997). 

Repeat Inspection - Maximum 10,500 

hour intervals. 

Do the inspections for these components in accordance with Component Maintenance 

Manual61-13-04. 

Do the inspections for these components in accordance with Component Maintenance 

Manual61-21-06. 

Parts manufactured after the effectivity date of AD 96-25-20 (February 7, 1997) have 

met the initial inspection requirements (paragraph 2.(a)) by an alternate method of 

compliance as approved by letter from the Manager, FAA Boston Aircraft Certification 

Office, on June 3, 1999. 

C. Ballscrew Spline Inspection 

(1) The internal spline of the ballscrew in the PCUs listed in Table AL-3 requires 

inspection to assure continued airworthiness. Component assemblies must be 

removed from service and subjected to the required inspections at intervals 

established in AD 95-22-12. The intervals are based on the time since new or time 

since last inspection. Do the inspection in accordance with the QHEQK section of 

chapter 61-22-00 (Propeller Control and Adapter). 

(2) It is the responsibility of the operator to monitor the flight hours for the PCU. 

Use or disclosure of this data is subject to restrictions on the TiUe Page of this document. 

Use or disclosure of this data is subject to restrictions on the Title Page of this document. 

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c Hamilton Sundstrand 

A United Technologies Company 

MAINTENANCE MANUAL 

14RF-9 

Table AL-3. Propeller Control Unit Components With Mandatory Inspections 

Item Part Number Inspection Interval 

(Flight Hours) 

Propeller Control Unit 782490-7, -12 See Airworthiness Directive 

(PCU) (Without Quill 95-22-12 

Damper, and without 

Secondary Drive Quill) 

Propeller Control Unit 782490-24 See Airworthiness Directive 

(PCU) (With Quill Damper, 95-22-12 

and without Secondary 

Drive Quill) 

D. PCU Primary Quill Torque Check 

(1) The PCU Part Numbers listed in Table AL-4 are equipped with a secondary drive 

quill and require an inspection to assure continued airworthiness. Component 

assemblies must be subjected to the required inspections at intervals established in 

AD 95-22-12. The intervals are based on the time since new or time since last 

inspection. Do the inspection in accordance with the CHECK section of 

chapter 61-22-00 (Propeller Control and Adapter). 

(2) It is the responsibility of the operator to monitor the flight hours for the PCU. 

Table AL-4. Propeller Control Unit Components With Mandatory Inspections 

Item Part Number Inspection Interval 

(Flight Hours) 

Propeller Control Unit (PCU) 782490-35, -46 See Airworthiness Directive 

95-22-12 

E. Hub Retaining Nut Check 

(1) Do a hub retaining nut torque check at an interval less than 500 hours in accordance 

with the "A" Inspection Checks, CHECK section, chapter 61-10-00. 

3. Special Instructions 

A If there is evidence of an overspeed, foreign object damage, lightning strike, or 

overtorque, do the inspection procedures in the CHECK section of chapter 61-10-00 

of this manual. Complete the appropriate report (Overspeed - Figure 504, 

Impact Damage- Figure 505, or Overtorque- Figure 506) and send a copy to the 

Hamilton Sundstrand address specified on it. Also, if necessary, make sure that a report 

of the incident is provided to the Federal Aviation Administration (FAA) in accordance 

with FAR 21.3 requirements. 

Use or disclosure of this data Is subject to restrictions on the Trtle Page of this document 

Use or disclosure of this data is subject to restrictions on the Title Page of this document. 

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